EP3640452A1 - Frontteil der antriebsgruppengondel eines luftfahrzeugs, der einen hauptweg zur ausbreitung von kräften zwischen einer lufteinlasslippe und einer rückwärtigen membran eines schalldämmpaneels umfasst - Google Patents

Frontteil der antriebsgruppengondel eines luftfahrzeugs, der einen hauptweg zur ausbreitung von kräften zwischen einer lufteinlasslippe und einer rückwärtigen membran eines schalldämmpaneels umfasst Download PDF

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Publication number
EP3640452A1
EP3640452A1 EP19203188.8A EP19203188A EP3640452A1 EP 3640452 A1 EP3640452 A1 EP 3640452A1 EP 19203188 A EP19203188 A EP 19203188A EP 3640452 A1 EP3640452 A1 EP 3640452A1
Authority
EP
European Patent Office
Prior art keywords
air intake
acoustic panel
intake lip
nacelle
rear skin
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP19203188.8A
Other languages
English (en)
French (fr)
Inventor
Alain Porte
Jacques Lalane
Julien SENTIER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP3640452A1 publication Critical patent/EP3640452A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to aircraft propulsion systems and more particularly to the nacelles of aircraft propulsion systems.
  • a propulsion unit is a device making it possible to generate a thrust, which constitutes the driving force of the aircraft equipped with the propulsion unit.
  • An aircraft propulsion system is shown by way of example at figure 1a .
  • FIG. 1b An example of a conventional installation of a nacelle N of a propulsion unit on an aircraft A is shown in figure 1b .
  • the nacelle conventionally comprises a front part P1 forming an air inlet.
  • the front part P1 has the role of capturing the air so as to ensure a regular flow towards the blower.
  • the nacelle also comprises a main part P2, constituting the rest of said nacelle.
  • the propulsion unit extends around an axis subsequently called the longitudinal axis L.
  • the front part P1 of the nacelle comprises an air inlet lip 1, which can be annular or substantially annular and which is arranged at its front end.
  • the concepts of "front” and “rear”, “anterior” and “posterior” as well as “upstream” and “downstream” are understood according to the direction of the air flow in the propulsion unit.
  • the air enters through the front of the propulsion unit, that is to say through the front part P1 of the nacelle and exits (after part of the air has served as oxidizer) by the rear of the propulsion unit, that is to say by the rear end of the main part P2.
  • the figure 2 represents a front part P1 of a propulsion unit according to a conventional configuration, conforming to the state of the art.
  • the air intake lip has a front frame 2 which is disposed at the rear of said air intake lip 1.
  • An internal structure comprising an acoustic panel 3, extends rearward the inner surface 11 of the air intake lip 1.
  • the acoustic panel 3 has the function of limiting the acoustic emissions of the propulsion unit by absorption of the acoustic waves generated in particular by the engine and the fan.
  • the acoustic waves which impact the resistive surface 31 (with respect to the nacelle) generally perforated of said acoustic panel are absorbed over a frequency range which depends on the constitution of the acoustic panel 3.
  • the acoustic panel also has a structural function , transmission of mechanical forces, explained below.
  • connection The way in which the connection is made between the air intake lip 1 and the acoustic panel 3 is conditioned by numerous design constraints.
  • this connection must allow a transmission of forces between the air intake lip and the acoustic panel 3, so that these forces are ultimately transmitted to a junction flange 5 allowing the connection of the front part P1 of the nacelle. to a structural element of the main part P2 of the nacelle.
  • the air intake lip generally includes thermal devices allowing it to be defrosted. These devices include, for example, a bypass of hot gases from the engine contained in the nacelle to the interior of the air intake lip 1.
  • the thermal transmission to the acoustic panel 3, which essentially occurs by radiation, should be limited as much as possible.
  • the junction between the air intake lip 1 and the acoustic panel 3 is made for example as shown in detail in the figure 3 .
  • the front frame 2 is linked to the internal wall of the air intake lip 1 (which forms the surface interior 11) in a contact zone located at the level of a foot 21 of said front frame 2.
  • the acoustic panel 3 is itself linked to the internal wall of the air intake lip behind said foot 21 of the frame front 2.
  • the acoustic panel 3 is linked to the internal wall of the air intake lip 1 in a contact zone situated behind the contact zone between the foot 21 of the front frame 2 and the lip air inlet 1.
  • the connection between the air intake lip 1 and the acoustic panel 3 is ensured by splicing a front crown 32 of the acoustic panel on the internal wall of the air intake lip.
  • the manufacturing process of the acoustic panel 3 (in particular for the deposition of the back skin on the panel), the geometric conformation of the assembly, as well as to a lesser extent the need to distribute the mechanical forces in the acoustic panel 3 imply that said acoustic panel 3 comprises a solid front zone 33, which is advantageously of triangular longitudinal section.
  • the mechanical forces coming from the air intake lip 1 are thus mainly transmitted to the acoustic panel 3 at the level of the interior surface 11 of the air intake lip 1 towards the resistive surface 31 of the acoustic panel 3.
  • the main force transmission channel is shown in figure 3 , by way of illustration, by a large arrow.
  • the objective of the invention is to enlarge as much as possible the acoustic treatment zone C towards the front of the nacelle, in particular by limiting the length of the junction zone B.
  • the invention relates to a front part of an aircraft propulsion unit nacelle, comprising an air intake lip disposed at a front end of said front part, an acoustic panel and a rigid connection between the acoustic panel and the air intake lip.
  • the front portion of the nacelle is configured so that a resistive surface of the acoustic panel extends an interior surface of the air intake lip.
  • the acoustic panel has a thickness delimited between its resistive surface and a rear skin, and said connection is formed between the air intake lip and said rear skin of the acoustic panel so as to form a main path of propagation of forces between said air intake lip and said rear skin.
  • the invention makes it possible to change the configuration of the connection between these elements, which eliminates certain design constraints, in particular in the front part of the acoustic panel. This ultimately allows the adoption of an acoustic panel with acoustic properties up to its front end, which can be approached from the front frame of the air intake lip, or even linked to said front frame.
  • the rigid connection between the acoustic panel and the air intake lip comprises an intermediate part, the section of which has a first connection branch on the air intake lip, a second connection branch on the rear skin of the acoustic panel, and a third branch rigidly linking the first branch to the second branch.
  • the intermediate piece may be an annular piece, made in one piece or by assembling several portions.
  • the intermediate piece may include stiffening ribs.
  • the intermediate piece can include an extra thickness inserted between a rear edge of the air intake lip and a front end of the resistive surface of the acoustic panel.
  • the air intake lip has a rear end comprising a wall extending the interior surface in the direction of the rear skin.
  • Said wall extending the interior surface can be extended by an annular surface linked to the rear skin of the acoustic panel so as to form the rigid connection between the air intake lip and the rear skin.
  • the extension wall extending the interior surface can be fixed to a front wall of the acoustic panel, said front wall being shaped to be in contact with the rear skin of the acoustic panel and fixed to said rear skin, so that the rigid connection between the air intake lip and the rear skin comprises the front wall.
  • the air intake lip may include a front frame comprising a foot linked to an internal surface of the air intake lip in the immediate vicinity of a front end of the acoustic panel.
  • the invention also relates to an aircraft propulsion unit comprising a nacelle comprising a front part and a main part, said front part being as previously described.
  • the invention finally relates to an aircraft comprising such a propulsion unit.
  • the figure 4 shows the detail of the junction between an air intake lip 1, in particular at its interior surface 11, and an acoustic panel 3, according to an embodiment of the invention.
  • the resistive surface 31 of the acoustic panel 3 must be in line with the interior surface 11, and a rigid connection must be formed between the air intake lip 1 and the acoustic panel 3, so as to transmit the forces from the air intake lip 1 to a junction flange 5 (not shown in the figure 4 ) allowing the junction of the front part of nacelle P1 with a main part P2.
  • the connection between the air intake lip 1 and the acoustic panel 3 is carried out in the embodiment shown using an intermediate piece 6.
  • the intermediate piece 6 is a rigid piece which is linked by a part to the air inlet lip 1 at its wall forming the interior surface 11, and secondly to the rear skin 34 of the acoustic panel 3.
  • the intermediate part 6 seen in section in a plane passing through the longitudinal axis L of the nacelle, has a first branch 61 which is linked to the air intake lip 1.
  • the intermediate piece 6 has a second branch 62 which is linked to the rear skin 34 of the panel acoustics 3.
  • the intermediate part 6 comprises a third branch 63 which rigidly connects the first branch 61 to the second branch 62.
  • the first branch 61 allows surface contact between the intermediate piece 6 and the air intake lip 1.
  • the second branch 62 allows surface contact between the intermediate piece 6 and the rear skin 34.
  • the different branches of the intermediate piece in fact correspond to crowns, insofar as the intermediate piece is generally annular, in accordance with the three-dimensional geometry of the front part of the nacelle .
  • the intermediate piece can be produced in a single piece or by assembly, in particular by splicing, of several portions.
  • the portions can for example be substantially in an arc of a circle (of fixed or variable curvature).
  • the intermediate piece 6 may include ribs 65, in order to improve its rigidity and its resistance.
  • the ribs 65 are distributed, preferably regularly, around the periphery of said intermediate piece 6.
  • connection between the intermediate part 6 and the air inlet lip 1 is direct, and can be achieved by various known means, for example by riveting, screwing, or gluing.
  • connection between the intermediate part 6 and the rear skin 34 implements an adjustment element 8 allowing mechanical adjustment between the intermediate piece 6 and the back skin 34.
  • the adjustment element 8 can be formed of a crown made of composite material.
  • connection between the intermediate piece 6 and the rear skin 34 can be achieved by various known means, for example by riveting, screwing, or gluing, and in particular by blind rivets.
  • the intermediate piece comprises in the example shown an excess thickness 64 interposed between a rear edge 12 of the lip air inlet 1 and a front end of the resistive surface 31 of the acoustic panel 3.
  • the additional thickness 64 is configured to catch up with the level between the first branch 61 and ensure continuity between the interior surface 11 and the resistive surface 31.
  • a seal 7 can be interposed between the additional thickness 64 and the acoustic panel 3, in order to guarantee a seal against fluids, in particular air.
  • connection thus implemented creates a main channel for transmitting forces between the air intake lip 1 and the acoustic panel 3 at its rear skin.
  • This main way of transmitting forces is shown in figure 4 , by way of illustration, by a large arrow.
  • connection thus implemented between the air intake lip 1 and the acoustic panel 3 at its rear skin 34 makes it possible to implement an acoustic panel having acoustic properties (absorption of acoustic waves) up to 'at its front end which is formed by a front wall 35.
  • the full front area of the acoustic panel is no longer necessary, because on the one hand the rear skin 35 does not need to be deposited on the front zone, triangular in longitudinal section, of the acoustic panel 3, and on the other hand because the forces undergone by the air intake lip are mainly transmitted to the rear skin 34.
  • the acoustic panel 3 may have in its front area a hollow or cellular form, or any other constitution allowing the absorption of acoustic waves.
  • the figure 4 has a honeycomb structure continued to the front end of the acoustic panel, while the Figures 5 and 6 represent a hollow structure at the front end of the acoustic panel.
  • the ways of ensuring that the acoustic panel retains acoustic properties up to its front end are interchangeable between the various embodiments of the invention.
  • the resistive surface 31 of the acoustic panel 3 can be perforated up to the front end of the acoustic panel 3. This makes it possible to extend the acoustic treatment zone C towards the front of the nacelle.
  • the length (in the longitudinal direction of the nacelle) of the junction area B is correspondingly reduced.
  • the air intake lip of the front part of the nacelle comprises a front frame 2.
  • the front frame 2 comprises a foot 21, which can thus be linked to the air intake lip 1 in the immediate vicinity of the front end of the acoustic panel.
  • the foot 21 of the front frame 2 is linked to the first branch 61 of the intermediate part 6, said first branch 61 being linked for its part to the air inlet lip 1.
  • the defrosting function provided in the air intake lip, in particular upstream of the front frame 2 can cause the circulation of air at around 200 ° C. in the air intake lip. It is preferable to limit the heat transmission behind the air intake lip 1, in particular to the acoustic panel 3.
  • the intermediate piece can be made of a thermal insulating material or include an insulating surface coating thermal.
  • an air gap 9 formed between the intermediate piece 63 (in this case the third branch 63 of the intermediate piece) and the front wall 35 makes it possible to limit this heat transmission.
  • the air gap 9 can be replaced by a blade of another gas or a vacuum gap to maximize its thermal insulation function.
  • the figure 5 illustrates a second embodiment of a front portion of the nacelle according to the invention.
  • the figure 5 represents more particularly, just like the figure 4 , the junction between the air inlet lip 1 and the acoustic panel 3 of the front part of the nacelle.
  • This second embodiment differs essentially from that shown in the figure 4 in that it does not include an intermediate piece 6. For the other elements, one can therefore refer to the description made above of the embodiment of the figure 4 .
  • the front wall 35 is shaped, and in particular curved, so as to be in contact and fixed in this contact zone to the rear skin 34.
  • the air intake lip 1 has a rear end comprising an extension wall 13 extending the interior surface 11 in the direction of the rear skin 34 of the acoustic panel 3.
  • the extension wall 13 extends substantially parallel to the front wall 35 of the acoustic panel.
  • the extension wall 13 is continued to further form an annular surface 14, which is superimposed and linked to the rear skin 34 (directly or with an adjustment element 8 as previously described).
  • the function of the second branch and the third branch of the intermediate piece are here fulfilled by the extension wall.
  • the annular surface 14 functionally replaces the second branch 62.
  • the connection implemented creates a main force transmission path (represented by a large arrow) between the air intake lip 1 and the acoustic panel 3 at its rear skin 34.
  • a space or an air space 9 can be provided between the extension wall 13 and the front wall 35 of the acoustic panel 3. This improves the thermal insulation between the air intake lip 1 and the acoustic panel 3.
  • a seal 7 (not shown in the figure 5 ) can be interposed between the air intake lip 1 and the acoustic panel 3, advantageously so as to ensure continuity between the interior surface 11 and the resistive surface 31.
  • the figure 6 illustrates a third embodiment of an aircraft front part in accordance with the invention, allowing the creation of a main force transmission channel (represented by a large arrow) between the air intake lip 1 and the acoustic panel 3 at its rear skin 34.
  • the figure 6 represents more particularly, just like the figures 4 and 5 , the junction between the air intake lip 1 and the acoustic panel 3 of the front part of the nacelle
  • the extension wall 13 of the air intake lip 1 is fixed to the front wall 35 of the acoustic panel 3.
  • the connection between said air intake lip 1 and the rear skin 34 is then carried out via the front wall 35 which is shaped, and in particular curved, so as to be in contact and fixed in this contact zone to the rear skin 34.
  • the contact between the extension wall 13 and the front wall 35 can promote thermal transmission by conduction, but, on the one hand, an insulating layer 81 (or an insulating coating) can be interposed, and d on the other hand, the insulation obtained can be satisfactory because most of the thermal transmission between the air intake lip 1 and the acoustic panel 3 is by radiation.
  • the figure 6 has a configuration of the front frame 2 which is particularly advantageous in this third embodiment, but which could be implemented in all of the embodiments of the invention, in order to greatly limit the length of the junction area B, and thus making it possible to maximize the acoustic treatment zone C (and / or the defrosting zone A).
  • the front frame is linked by its foot 21 to the extension wall 13 of the air intake lip 1.
  • all the connections between the air intake lip 1 and the acoustic panel 3 are made at the wall front 35 of the acoustic panel, which makes it possible to use no portion of the internal surface 11 of the nacelle for the production of these connections.
  • connection between the air intake lip and the acoustic panel can be carried out between the front frame 2 of the air intake lip and the acoustic panel only, at its front wall 35, a portion of said front frame 2 extending behind its connecting foot 21 connecting it to the internal wall 11 of the nacelle.
  • the figure 7 shows a variant according to the invention, of the junction between an air inlet 1 and an acoustic panel 3.
  • This variant is illustrated on the basis of the embodiment of the figure 6 , but it is applicable to all of the embodiments of the invention.
  • the foot 21 of the front frame 2 is linked to the internal wall of the air intake lip 1, and is extended by an end wall of the front frame 22.
  • the end wall of the front frame 22 extends opposite the extension wall 13, at a distance from the latter.
  • the front frame end wall 22 provides thermal protection against radiation at the junction between the air inlet 1 and the acoustic panel 3.
  • This function can be obtained alternatively by an attached part attached to the air intake lip.
  • FIGS. 8 and 9 represent two variants of an embodiment of the invention in which the acoustic panel 3 has a particular conformation facilitating the connection between the air intake lip and said acoustic panel which is produced at the rear skin 34 of the acoustic panel 3.
  • connection between the air intake lip 1 and the rear skin 34 is produced at the level of an extension wall 13 extending the interior surface 11 on said rear skin 34.
  • an extension portion 23 of the front frame 2 extends over said rear skin to which it is linked, behind its foot 21 which is linked to the internal wall 11 of the nacelle.
  • connection can be made directly, with the optional presence near an intermediate adjustment element, or via a intermediate piece that can be configured in particular to ensure continuity between the inner surface 11 and the resistive surface 31, for example by virtue of an additional thickness of the intermediate piece.
  • the front part of the aircraft propulsion assembly nacelle thus developed in the invention allows, by an optimized connection configuration between the air intake lip and the acoustic panel, to maximize the acoustic treatment area at the inside the nacelle, extending this area towards the front of the nacelle.
  • the configuration proposed in the invention also makes it possible to create, at the anterior end of the acoustic panel, a force transmission channel towards the rear skin of the acoustic panel.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
EP19203188.8A 2018-10-18 2019-10-15 Frontteil der antriebsgruppengondel eines luftfahrzeugs, der einen hauptweg zur ausbreitung von kräften zwischen einer lufteinlasslippe und einer rückwärtigen membran eines schalldämmpaneels umfasst Withdrawn EP3640452A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1859626A FR3087489B1 (fr) 2018-10-18 2018-10-18 Partie anterieure de nacelle de groupe propulsif d'aeronef comportant une voie principale de propagation d'efforts entre une levre d'entree d'air et une peau arriere d'un panneau acoustique

Publications (1)

Publication Number Publication Date
EP3640452A1 true EP3640452A1 (de) 2020-04-22

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Application Number Title Priority Date Filing Date
EP19203188.8A Withdrawn EP3640452A1 (de) 2018-10-18 2019-10-15 Frontteil der antriebsgruppengondel eines luftfahrzeugs, der einen hauptweg zur ausbreitung von kräften zwischen einer lufteinlasslippe und einer rückwärtigen membran eines schalldämmpaneels umfasst

Country Status (4)

Country Link
US (1) US11649062B2 (de)
EP (1) EP3640452A1 (de)
CN (1) CN111071462A (de)
FR (1) FR3087489B1 (de)

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US20200122851A1 (en) 2020-04-23
CN111071462A (zh) 2020-04-28
FR3087489A1 (fr) 2020-04-24
US11649062B2 (en) 2023-05-16

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